Abstract: A combustor includes an upstream surface that extends radially across at least a portion of the combustor, a downstream surface that extends radially across at least a portion of the combustor and is axially separated from the upstream surface, and a plurality of tubes that extend through the downstream surface. A resonator is upstream from at least one of the tubes, and a fluid passage extends through the resonator and into the least one tube.

Abstract: A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.

Abstract: A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber.

Abstract: An igniter tip for a combustion system is provided. The igniter tip may include a central electrode; an insulator sleeve about the central electrode; and an outer electrode about the insulator sleeve, the outer electrode including a tubular wall having a cooling passage extending within the tubular wall, the cooling passage including an entrance opening and an exit opening to an exterior of the outer electrode. A combustion system may include the igniter tip.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.

Abstract: Embodiments of the present application can provide systems and methods for dampening combustor dynamics. According to one embodiment, the system may include a micromixer. The system may also include at least one annular resonator disposed within the micromixer adjacent to a cap face plate or an impingement plate of the micromixer. The at least one annular resonator may include a first side including a number of holes forming a cold side hole pattern, a second side including a number of holes forming a hot side hole pattern, and a cavity substantially defined by the first side and the second side.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and fuel injectors provide fluid communication to the combustion chamber. A distribution manifold circumferentially surrounds the fuel injectors and defines an annular plenum. A fluid passage through the distribution manifold provides fluid communication through the distribution manifold. A radial cross-sectional area of the annular plenum varies around the flow sleeve. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds fuel injectors circumferentially arranged around the combustion chamber, and changing at least one of a pressure or flow rate of the diverted portion of the working fluid.

Abstract: One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.

Abstract: A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and a plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the distribution manifold provides fluid communication through the distribution manifold to the plurality of fuel injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber and diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds a plurality of fuel injectors circumferentially arranged around the combustion chamber.

Abstract: Embodiments of the present application can provide systems and methods for a micromixer combustion head end assembly. The micromixer may include one or more base nozzle structures. The base nozzle structures may include coaxial tubes. The coaxial tubes may include an inner tube and an outer tube. The micromixer may also include one or more segmented mixing tube bundles at least partially supported by a respective base nozzle structure. Moreover, the micromixer may include an end cap assembly disposed about the one or more segmented mixing tube bundles.

Abstract: A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner.

Abstract: A trapped vortex fuel injector includes a main body having an annular portion and a semi-annular portion coaxially aligned with the annular portion. The semi-annular portion extends downstream from the annular portion. An inner wall and an opposing outer wall of the main body extend between the annular and semi-annular portions. The annular portion at least partially defines a combustion air flow passage through the trapped vortex fuel injector. The semi-annular portion defines a trapped vortex pre-mix zone downstream from the combustion air flow passage. The main body further defines a fuel circuit that is fully circumscribed within the main body and that extends between the annular portion and the semi-annular portion. A plurality of fuel injection ports provide for fluid communication between the fuel circuit and the trapped vortex pre-mix zone. The main body may be fabricated using an additive manufacturing process.

Abstract: A system for cooling a fuel injector extending into a combustion gas flow field includes a liner that defines a combustion gas flow path within a combustor and a fuel injector that extends through the liner. The fuel injector includes a main body having an annular first portion that extends outward from the liner and a second portion that extends from the first portion inward into the combustion gas flow path. The main body defines a cooling channel that is fully circumscribed within the main body and that extends between the first portion and the second portion. A cooling air inlet is defined within the annular first portion and is in fluid communication with the cooling channel. A cooling air outlet is in fluid communication with the cooling channel and is defined within the second portion downstream from the cooling air inlet.

Abstract: A fuel nozzle includes a center body that is at least partially surrounded by an outer shroud. The outer shroud is radially spaced from the center body to define a pre-mix flow passage therebetween. The outer shroud includes a main body that defines an inner side portion, an outer side portion and a forward end portion that is axially separated from an aft end portion. The main body further defines a cooling channel that is fully circumscribed between the inner side portion and the outer side portion and that extends at least partially between the forward end portion and the aft end portion. The main body also defines a cooling air inlet that is in fluid communication with the cooling channel and a cooling air outlet that is in fluid communication with the cooling channel downstream from the cooling air inlet.

Abstract: A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube.

Abstract: Embodiments of the present application can provide systems and methods for a coaxial fuel supply for a micromixer. According to one embodiment, the micromixer may include an elongated base nozzle structure, a number of mixing tubes in communication with the elongated base nozzle structure, and an air inlet configured to supply the plurality of mixing tubes with air. The elongated base nozzle structure may be configured to supply a fuel to the mixing tubes.

Abstract: A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.

Abstract: Disclosed herein are apparatuses, methods, and systems for transition piece contouring. In an embodiment, a high thermal stress section of a transition piece and a low thermal stress section of a transition piece is a determined. The low thermal stress section of the transition piece may be contoured to intercept hot gas flow.

Abstract: A transition piece aft frame is provided and includes a manifold having an interior that is receptive of fuel and formed to define fuel injection holes configured to inject the received fuel from the manifold interior toward a main flow of products of combustion flowing through the manifold. The manifold includes a main body having an interior facing surface that faces the main flow of the products of the combustion and along which the fuel injection holes are defined.